CN108590864A - A kind of small-sized missile turbojet engine cartridge start method and device - Google Patents
A kind of small-sized missile turbojet engine cartridge start method and device Download PDFInfo
- Publication number
- CN108590864A CN108590864A CN201810180523.7A CN201810180523A CN108590864A CN 108590864 A CN108590864 A CN 108590864A CN 201810180523 A CN201810180523 A CN 201810180523A CN 108590864 A CN108590864 A CN 108590864A
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- CN
- China
- Prior art keywords
- turbojet engine
- adaptive
- compressor
- flapper valve
- combustion chamber
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
The present invention provides a kind of small-sized missile turbojet engine cartridge start devices, including adaptive flapper valve, compressor, fuel nozzle, gunpowder packet, fire rod, turbine, the adaptive flapper valve is arranged before the compressor of turbojet engine, the other side of the compressor is equipped with combustion chamber, fuel nozzle and fire rod are installed in the combustion chamber, the top of the fire rod is equipped with gunpowder packet, and the other end of the combustion chamber is connected with turbine.Advantageous effect of the present invention：The complicated problem of the starting of missile turbojet engine in the prior art can be simplified, facilitate the starting of missile turbojet engine, and reduce cost.
Description
Technical field
The invention belongs to technical field of engines, more particularly, to a kind of small-sized missile turbojet engine cartridge start method
And device.
Background technology
Turbojet engine is advanced using the gas push engine of jet pipe high speed discharge, and speed is fast, can be compared with after shooting
Solid engines far firing range, so being applied on some Tactical Cruise Missiles.However the starting system of missile turbojet engine
Unite more complicated, in addition to external compression air actuation, it is electrically actuated other than, the most commonly used is cartridge start modes.
Cartridge start needs special ignition system, saucisson, it is also necessary to be designed specially on turbojet engine rotor
Play movable vane piece etc..For the missile turbojet engine of first use, this start mode is complicated and cost is higher.
Invention content
In view of this, the present invention is directed to propose a kind of small-sized missile turbojet engine cartridge start method and device, with solution
The certainly shortcoming of the above problem.
In order to achieve the above objectives, the technical proposal of the invention is realized in this way：
A kind of small-sized missile turbojet engine cartridge start method, includes the following steps：
A. being arranged before the compressor of turbojet engine has oneself for the function of being automatically turned on according to compressor initial vacuum degree
Flapper valve is adapted to, before engine start, adaptive flapper valve is in off state；
B. after obtaining engine startup instruction, the indoor fire rod that burns powers on, but does not supply fuel oil, at this time by
Fire rod lights the gunpowder packet on its top；
C. with the rising of secondary speed, compressor high speed rotation is driven, pressure drastically reduces before compressor, and forms one
The vacuum degree of fixed number value opens the suction of adaptive flapper valve, and fresh air enters combustion chamber；
D. turbojet engine rotating speed rises to can start fuel feeding with the rotating speed of normal ignition, fuel nozzle, and fire rod is again
Igniting, turbojet engine can work normally.
It is a kind of to realize small-sized missile turbojet engine cartridge start as described above the present invention also provides second embodiment
The device of method, including adaptive flapper valve, compressor, fuel nozzle, gunpowder packet, fire rod, turbine, the adaptive baffle
Valve is arranged before the compressor of turbojet engine, and the other side of the compressor is equipped with combustion chamber, is equipped in the combustion chamber
The top of fuel nozzle and fire rod, the fire rod is equipped with gunpowder packet, and the other end of the combustion chamber is connected with turbine, described
Adaptive flapper valve has the function of being automatically turned on according to compressor initial vacuum degree.
Further, the housing material of the gunpowder packet is decomposable asymmetric choice net material.
Further, the fire rod is connect with power supply.
Compared with the existing technology, small-sized missile turbojet engine cartridge start method and device of the present invention have with
Lower advantage：
Small-sized missile turbojet engine cartridge start method and device of the present invention can simplify the prior art and be hit by a bullet
With the problem that the starting of turbojet engine is complicated, the starting of missile turbojet engine is facilitated, and reduce cost.
Description of the drawings
The attached drawing for constituting the part of the present invention is used to provide further understanding of the present invention, schematic reality of the invention
Example and its explanation are applied for explaining the present invention, is not constituted improper limitations of the present invention.In the accompanying drawings：
Fig. 1 is the small-sized missile turbojet engine cartridge start apparatus structure schematic diagram described in the embodiment of the present invention；
Fig. 2 is the structural schematic diagram of the adaptive baffle the valve opening state described in the embodiment of the present invention；
Fig. 3 is the driving structure schematic diagram of the adaptive flapper valve described in the embodiment of the present invention.
Reference sign：
The adaptive flapper valves of 1-；2- compressors；3- fuel nozzles；4- gunpowder packets；5- fire rodes；6- turbines；7- is adaptive
Inlet duct outlet section；The combustion chambers 8-；9- gas springs；10- cranks；The adaptive inlet duct inducers of 11-.
Specific implementation mode
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
Can also be electrical connection to be mechanical connection；It can be directly connected, can also indirectly connected through an intermediary, Ke Yishi
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood by concrete condition
Concrete meaning in the present invention.
The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
A kind of small-sized missile turbojet engine cartridge start method, includes the following steps：
A. setting has the function of being automatically turned on according to 2 initial vacuum degree of compressor before the compressor of turbojet engine 2
Adaptive flapper valve 1, before engine start, adaptive flapper valve 1 is in off state；
B. after obtaining engine startup instruction, the fire rod 5 in combustion chamber 8 powers on, but does not supply fuel oil, at this time
Gunpowder packet 4 is lighted by fire rod 5；
C. with the rising of 6 rotating speed of turbine, 2 high speed rotation of compressor is driven, pressure drastically reduces before compressor 2, and shape
At the vacuum degree of certain numerical value, the suction of adaptive flapper valve 1 is opened, fresh air enters combustion chamber；
D. turbojet engine rotating speed, which rises to, to start fuel feeding with the rotating speed of normal ignition, fuel nozzle 3, and fire rod 5 is again
Secondary igniting, turbojet engine can work normally.
The present invention also provides another embodiments, as depicted in figs. 1 and 2, a kind of small-sized missile turbojet engine gunpowder
Dynamic device, including adaptive flapper valve 1, compressor 2, fuel nozzle 3, gunpowder packet 4, fire rod 5, turbine 6, the adaptive gear
Plate valve 1 is arranged before compressor 2, and the other side of the compressor 2 is equipped with combustion chamber 8, and combustion is equipped in the combustion chamber 8
The top of oil burner nozzle 3 and fire rod 5, the fire rod 5 is equipped with gunpowder packet 4, and the other end of the combustion chamber 8 is connected with turbine 6,
The adaptive flapper valve 1 has the function of being automatically turned on according to 2 initial vacuum degree of compressor.
The housing material of the gunpowder packet 4 is decomposable asymmetric choice net material.
The fire rod 5 is connect with power supply.
1 domed harden structure of the adaptive flapper valve, 4 domed harden structure of the valve plate, and bottom are equipped with valve shaft, institute
It states valve shaft one end and is inserted into adaptive 11 inner wall of inlet duct inducer, the other end passes through adaptive inlet duct side wall and and crank
10 connections.As shown in figure 3, the crank is also associated with the piston end of gas spring 9, the pressure cylinder end of the gas spring 9 is connected to
At adaptive 11 outer wall of inlet duct inducer, the adaptive flapper valve 1 is fitted in the end of adaptive inlet duct outlet section 7
On face, and rotated in the internal cavities of adaptive inlet duct outlet section 7,1 bottom of adaptive flapper valve with it is adaptive
7 bottom connection of inlet duct outlet section touches.The adaptive flapper valve 1 has unidirectional open function.
The gas spring 9 and angle of the crank 10 in locking state are 15 °.
The inner passage of the adaptive inlet duct outlet section 7 is centered on 4 bottom end of valve plate, from adaptive flapper valve 1
Vertical position rise and match with the exterior contour of adaptive flapper valve 1 within the scope of 20 °, and size is consistent, this make from
Within the scope of adapt to 1 initial rotation of flapper valve 20 °, air cannot be from adaptive flapper valve 1 and adaptive inlet duct outlet section 7
Passing through at the gap of inner wall, gas spring 9 is constantly in compressive state, when adaptive flapper valve 1 is closed, gas spring 9 and crank
10 form a smaller angle, and the compressing force of gas spring 9 is larger；When adaptive flapper valve 1 is opened, gas spring 9 and crank 10
One is formed compared with mitre, the compressing force of gas spring 9 is smaller.
The course of work of the adaptive flapper valve 1 is as follows：
Adaptive flapper valve 1 is closed when beginning.Pressure is with compressor before the compressor of turbojet engine
The rotating speed of impeller rises and reduces, and when quickly forming certain vacuum degree, the air inside adaptive inlet duct outlet section 7
Pressure also reduces, and adaptive flapper valve 1 then rotates clockwise, and overcomes the pretightning force of gas spring 9, makes gas spring 9 and crank 10
Angle reduce, and cross 0 °.Increase as adaptive flapper valve 1 rotates clockwise angle, at this moment gas spring 9 is by auxiliary pushing
Adaptive flapper valve 1 rotates clockwise, and adaptive flapper valve 1 is opened completely, when adaptive flapper valve 1 in the open state,
The inner wall of adaptive flapper valve 1 and adaptive inlet duct outlet section 7 completely attaches to, and fresh air enters combustion chamber 8.
The course of work of the present embodiment is as follows：
Before engine start, adaptive flapper valve 1 is in off state；After engine start, fire rod 5 powers on, but
Fuel oil is not supplied, gunpowder packet 4 is lighted by fire rod 5 at this time, gunpowder packet 4 expands in the combustion chamber, and pressure-air is exported from turbine 6
Discharge；With the rising of 6 rotating speed of turbine, 2 high speed rotation of compressor is driven, pressure drastically reduces before compressor 2, and quickly forms
The vacuum degree of certain numerical value opens the suction of adaptive flapper valve 1, and fresh air enters combustion chamber 8, at this point, turbojet engine rotating speed
Fuel feeding can be started with the rotating speed of normal ignition, fuel nozzle 3 by having increased to, and fire rod 5 is lighted a fire again, and turbojet engine can
Normal work.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention god.
Claims (4)
1. a kind of small-sized missile turbojet engine cartridge start method, which is characterized in that include the following steps：
A. setting has the adaptive of the function of being automatically turned on according to compressor initial vacuum degree before the compressor of turbojet engine
Flapper valve, before engine start, adaptive flapper valve is in off state；
B. after obtaining engine startup instruction, the indoor fire rod that burns powers on, but does not supply fuel oil, at this time by lighting a fire
Stick lights the gunpowder packet on its top；
C. with the rising of secondary speed, compressor high speed rotation is driven, pressure drastically reduces before compressor, and forms a fixed number
The vacuum degree of value opens the suction of adaptive flapper valve, and fresh air enters combustion chamber；
D. turbojet engine rotating speed, which rises to, to start fuel feeding with the rotating speed of normal ignition, fuel nozzle, and fire rod is lighted a fire again,
Turbojet engine can work normally.
2. a kind of small-sized missile turbojet engine cartridge start device, it is characterised in that：Including adaptive flapper valve, compressor,
Fuel nozzle, gunpowder packet, fire rod, turbine, the adaptive flapper valve are arranged before the compressor of turbojet engine, the pressure
The other side of mechanism of qi is equipped with combustion chamber, is equipped with fuel nozzle and fire rod in the combustion chamber, the top of the fire rod is set
There are gunpowder packet, the other end of the combustion chamber to be connected with turbine, the adaptive flapper valve has according to compressor initial vacuum degree
The function of automatic opening.
3. a kind of small-sized missile turbojet engine cartridge start device according to claim 2, it is characterised in that：The fire
The housing material of pack is decomposable asymmetric choice net material.
4. a kind of small-sized missile turbojet engine cartridge start device according to claim 2, it is characterised in that：The point
Lighted torch is connect with power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810180523.7A CN108590864B (en) | 2018-03-05 | 2018-03-05 | Powder starting method and device of turbojet engine for small-sized bomb |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810180523.7A CN108590864B (en) | 2018-03-05 | 2018-03-05 | Powder starting method and device of turbojet engine for small-sized bomb |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108590864A true CN108590864A (en) | 2018-09-28 |
| CN108590864B CN108590864B (en) | 2019-12-20 |
Family
ID=63625714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810180523.7A Active CN108590864B (en) | 2018-03-05 | 2018-03-05 | Powder starting method and device of turbojet engine for small-sized bomb |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108590864B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN112576378A (en) * | 2020-12-14 | 2021-03-30 | 江西洪都航空工业集团有限责任公司 | Gas turbine engine with automatic separation starting turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5913807A (en) * | 1998-03-30 | 1999-06-22 | Williams International Corp. L.L.C. | Turbojet engine start system |
| US20070095047A1 (en) * | 2005-11-03 | 2007-05-03 | Simyon Rozenberg | Fuel ignition system for jet engine staring |
| CN106342115B (en) * | 2011-01-04 | 2013-12-11 | 哈尔滨东安发动机（集团）有限公司 | Engine firer product starting system |
| CN204041245U (en) * | 2014-08-15 | 2014-12-24 | 中国燃气涡轮研究院 | The nozzle pipe line structure that a kind of powder gas starts |
| CN105736148A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gunpowder starting device of aircraft engine |
-
2018
- 2018-03-05 CN CN201810180523.7A patent/CN108590864B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5913807A (en) * | 1998-03-30 | 1999-06-22 | Williams International Corp. L.L.C. | Turbojet engine start system |
| US20070095047A1 (en) * | 2005-11-03 | 2007-05-03 | Simyon Rozenberg | Fuel ignition system for jet engine staring |
| CN106342115B (en) * | 2011-01-04 | 2013-12-11 | 哈尔滨东安发动机（集团）有限公司 | Engine firer product starting system |
| CN204041245U (en) * | 2014-08-15 | 2014-12-24 | 中国燃气涡轮研究院 | The nozzle pipe line structure that a kind of powder gas starts |
| CN105736148A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gunpowder starting device of aircraft engine |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN112576378A (en) * | 2020-12-14 | 2021-03-30 | 江西洪都航空工业集团有限责任公司 | Gas turbine engine with automatic separation starting turbine |
| CN112576378B (en) * | 2020-12-14 | 2023-03-24 | 江西洪都航空工业集团有限责任公司 | Gas turbine engine with automatic separation starting turbine |
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| Publication number | Publication date |
|---|---|
| CN108590864B (en) | 2019-12-20 |
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